ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 200,000 Max Cl/Cd: 78.35 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor07-il-200000.txt Download as CSV file: xf-hor07-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR07 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4037 0.09796 0.09461 -0.0056 1.0000 0.0404
-7.500 -0.3973 0.09488 0.09156 -0.0072 1.0000 0.0415
-7.250 -0.3912 0.09180 0.08851 -0.0093 1.0000 0.0428
-7.000 -0.3810 0.08837 0.08511 -0.0135 1.0000 0.0445
-6.750 -0.3581 0.08446 0.08121 -0.0275 1.0000 0.0465
-6.500 -0.3333 0.07999 0.07671 -0.0367 1.0000 0.0468
-6.250 -0.3291 0.07429 0.07108 -0.0359 1.0000 0.0478
-6.000 -0.3175 0.07150 0.06832 -0.0345 1.0000 0.0490
-5.750 -0.3011 0.06859 0.06544 -0.0358 1.0000 0.0506
-5.500 -0.2806 0.06521 0.06207 -0.0395 1.0000 0.0530
-5.250 -0.2205 0.05839 0.05499 -0.0605 1.0000 0.0591
-5.000 -0.2108 0.05370 0.05042 -0.0606 0.9953 0.0607
-4.750 -0.1801 0.05159 0.04831 -0.0623 0.9840 0.0647
-4.500 -0.1200 0.04435 0.04076 -0.0770 0.9721 0.0742
-4.250 -0.0858 0.04180 0.03817 -0.0800 0.9566 0.0777
-4.000 -0.0067 0.02318 0.01789 -0.0980 0.9508 0.0431
-3.750 0.0336 0.01897 0.01279 -0.1009 0.9342 0.0406
-3.500 0.0651 0.01720 0.01055 -0.1013 0.9151 0.0414
-3.250 0.0929 0.01616 0.00919 -0.1008 0.8970 0.0438
-3.000 0.1198 0.01533 0.00804 -0.1000 0.8804 0.0476
-2.750 0.1470 0.01424 0.00685 -0.0995 0.8651 0.0528
-2.250 0.2024 0.01304 0.00546 -0.0987 0.8364 0.0802
-2.000 0.2305 0.01276 0.00519 -0.0984 0.8227 0.1105
-1.750 0.2585 0.01259 0.00503 -0.0982 0.8093 0.1575
-1.500 0.2861 0.01260 0.00497 -0.0979 0.7963 0.1878
-1.250 0.3137 0.01255 0.00491 -0.0977 0.7841 0.2091
-1.000 0.3414 0.01251 0.00480 -0.0974 0.7730 0.2284
-0.750 0.3693 0.01244 0.00470 -0.0972 0.7622 0.2498
-0.500 0.3975 0.01237 0.00465 -0.0972 0.7511 0.2754
-0.250 0.4257 0.01224 0.00457 -0.0971 0.7411 0.2992
0.000 0.4540 0.01208 0.00445 -0.0971 0.7316 0.3319
0.250 0.4825 0.01183 0.00444 -0.0972 0.7213 0.3876
0.500 0.5024 0.01028 0.00423 -0.0951 0.7126 1.0000
0.750 0.5311 0.01041 0.00417 -0.0950 0.7027 1.0000
1.000 0.5597 0.01053 0.00418 -0.0950 0.6924 1.0000
1.250 0.5880 0.01067 0.00419 -0.0949 0.6829 1.0000
1.500 0.6164 0.01079 0.00422 -0.0948 0.6725 1.0000
1.750 0.6448 0.01090 0.00428 -0.0948 0.6615 1.0000
2.000 0.6730 0.01103 0.00435 -0.0947 0.6511 1.0000
2.250 0.7011 0.01116 0.00440 -0.0946 0.6409 1.0000
2.500 0.7294 0.01128 0.00449 -0.0945 0.6288 1.0000
2.750 0.7575 0.01142 0.00460 -0.0945 0.6169 1.0000
3.000 0.7855 0.01157 0.00473 -0.0944 0.6052 1.0000
3.250 0.8135 0.01174 0.00485 -0.0942 0.5939 1.0000
3.500 0.8414 0.01191 0.00499 -0.0941 0.5818 1.0000
3.750 0.8692 0.01207 0.00517 -0.0940 0.5682 1.0000
4.000 0.8967 0.01221 0.00528 -0.0938 0.5523 1.0000
4.250 0.9239 0.01228 0.00534 -0.0935 0.5287 1.0000
4.500 0.9507 0.01241 0.00540 -0.0932 0.5047 1.0000
4.750 0.9779 0.01260 0.00558 -0.0930 0.4824 1.0000
5.000 1.0047 0.01285 0.00579 -0.0927 0.4605 1.0000
5.250 1.0311 0.01316 0.00603 -0.0925 0.4328 1.0000
5.500 1.0572 0.01351 0.00633 -0.0922 0.3934 1.0000
5.750 1.0777 0.01494 0.00694 -0.0916 0.2321 1.0000
6.000 1.0927 0.01797 0.00894 -0.0908 0.0795 1.0000
6.250 1.1155 0.01909 0.01011 -0.0902 0.0696 1.0000
6.500 1.1373 0.02025 0.01134 -0.0894 0.0649 1.0000
6.750 1.1595 0.02125 0.01243 -0.0886 0.0616 1.0000
7.000 1.1807 0.02236 0.01360 -0.0877 0.0592 1.0000
7.250 1.2006 0.02365 0.01490 -0.0866 0.0570 1.0000
7.500 1.2179 0.02569 0.01690 -0.0852 0.0546 1.0000
7.750 1.2401 0.02683 0.01813 -0.0843 0.0535 1.0000
8.000 1.2625 0.02812 0.01955 -0.0833 0.0525 1.0000
8.250 1.2853 0.02958 0.02113 -0.0824 0.0515 1.0000
8.500 1.3080 0.03106 0.02275 -0.0816 0.0499 1.0000
8.750 1.3295 0.03236 0.02414 -0.0808 0.0473 1.0000
9.000 1.3499 0.03416 0.02593 -0.0802 0.0443 1.0000
9.250 1.3692 0.03670 0.02875 -0.0792 0.0416 1.0000
9.500 1.3876 0.03813 0.03046 -0.0778 0.0391 1.0000
9.750 1.4053 0.03999 0.03251 -0.0766 0.0366 1.0000
10.000 1.4212 0.04203 0.03457 -0.0757 0.0341 1.0000
10.250 1.4291 0.04598 0.03895 -0.0737 0.0318 1.0000
10.500 1.4363 0.04853 0.04193 -0.0712 0.0301 1.0000
10.750 1.4400 0.05198 0.04576 -0.0687 0.0290 1.0000
11.000 1.4392 0.05558 0.04971 -0.0660 0.0283 1.0000
11.250 1.4323 0.05936 0.05385 -0.0630 0.0279 1.0000
11.500 1.4165 0.06317 0.05796 -0.0592 0.0279 1.0000
11.750 1.3954 0.06740 0.06250 -0.0562 0.0282 1.0000
12.000 1.3726 0.07232 0.06771 -0.0546 0.0285 1.0000
12.250 1.3485 0.07785 0.07348 -0.0545 0.0288 1.0000
12.500 1.3237 0.08393 0.07979 -0.0556 0.0292 1.0000
12.750 1.2987 0.09055 0.08663 -0.0577 0.0296 1.0000
13.000 1.2734 0.09777 0.09404 -0.0609 0.0300 1.0000
13.250 1.2480 0.10566 0.10209 -0.0651 0.0304 1.0000
13.500 1.2229 0.11424 0.11082 -0.0702 0.0309 1.0000
13.750 1.1986 0.12354 0.12023 -0.0761 0.0314 1.0000
14.000 1.1775 0.13304 0.12979 -0.0817 0.0321 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ONERA HOR07 AIRFOIL (hor07-il)